Aerodynamic Performance Research And Wind Tunnel Test Of Two-dimensional And Variable Geometry Tbcc Inlet

The two-dimensional TBCC intake is with simple variable geometry,it is easy to be integrated with aircraft design.Based on requirements of the two-dimensional TBCC inlet Mach number working,a variable geometry mechanism suitable for wide Mach number range of inlet is studied.Numerical simulations were used to obtain the flow characteristics and performance parameters of inlet at different working modes.The steady-state simulation method is used to study self-starting process in the design state of inlet,and a wind tunnel test is performed to verify self-starting performance of inlet.The main contents are as follows:1.Designed a two-dimensional TBCC mixed pressure inlet.The shoulder of internal pressure section adopts a curved surface transition method.By studying the shoulder profiles with different tensions,the flow characteristics and performance changes of the air inlets at different shoulder profiles are obtained;Three types of variable geometry mechanisms for adjusting the throat area were designed,and the working principles of the three types of variable geometry mechanisms were given.By comparing the three variable geometry plans,plan c is reliable in structure,easy to adjust,and more suitable for two-dimensional variable geometry inlet.2.Numerical simulation is used to study the aerodynamic performance of inlet at typical Mach number.In Ma3.0 ? 4.0 ramjet mode,the flow coefficient is between 0.663 ? 0.839,and the total outlet pressure recovery is between 0.523 ? 0.713.Under the maximum back pressure working characteristics,the steady-state distortion index is less than 1.5%;in Ma0.8 ? 1.5 turbine mode,the total captured flow coefficient of the inlet is between 0.295 ? 0.477,and excess flow is taken out by the stamped channel.The flow coefficient of the turbine exit is between 0.227 and 0.3,and the total pressure recovery is between 0.887 and 0.975.During transition mode,appropriately increasing the opening of turbine channel is conducive to improving the flow separation of turbine channel,and the performance of ramjet outlet does not decrease mush.3.Using a steady simulation method,the numerical simulation of self-starting of inlet is carried out under the designed state,and the flow changes from unstarted state to the stated state of inlet under different internal contraction ratios are analyzed,and the performance parameter changes at the throat is analyzed.;The wind tunnel test verification is performed for the self-starting process of inlet.The test results agree well with the numerical simulation results,and the parameter changes is basically consistent.The simulation methods used in this paper has credibility.